Abstract: The invention relates to a method for mounting a rotor blade with a rotor blade shell and an internal space defined by the rotor blade shell, by at least one rotor blade clamp being applied around the outside of the rotor blade shell, by means of which at least one clamping force is exerted from the outside to the rotor blade shell, directed into the internal space by at least one expansion device being introduced into the internal space, by the expansion device inside the internal space being moved into at least one segment of the rotor blade around which the at least one rotor blade clamp is applied, by the at least one expansion device being expanded inside the at least one segment until at least one outwardly-acting counteracting force is exerted from the inside on the rotor blade shell.

Abstract: A spacing arrangement for a gas turbine engine 10. The spacing arrangement being arranged such that as a rotor blade 26 of a compressor 13 rotates, the rotor disc 28 will move outwards and forwards to maintain a substantially constant gap 36 between the rotor blade 26 and an inclined casing 20.

Abstract: A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.

Abstract: A turbine vane assembly includes a turbine vane having first and second shrouds with an elongated airfoil extending between. Each end of the airfoil transitions into a shroud at a respective junction. Each of the shrouds has a plurality of cooling passages, and the airfoil has a plurality of cooling passages extending between the first and second shrouds. A substantially flat inner plate and an outer plate are coupled to each of the first and second shrouds so as to form inner and outer plenums. Each inner plenum is defined between at least the junction and the substantially flat inner plate; each outer plenum is defined between at least the substantially flat inner plate and the outer plate. Each inner plenum is in fluid communication with a respective outer plenum through at least one of the cooling passages in the respective shroud.

Abstract: A self-guiding wind turbine made of two reinforced parallel girders whose side center of thrust is displaced from the column axis where it is supported and turns. Its dihedral-shaped two-bladed rotor is self-stabilizing since its center of thrust is behind its center of gravity and the guiding axis of the turbine, thus improving self-guiding whilst in motion. The axial thrust is controlled, whilst the head and rotor are tilting, hydraulically by counter-pressure, ensuring they do not surpass the power collected and the moments on the structure, shoe and ground. The self-guiding structure can tilt hydraulically lowering its head and rotor and facilitating its assembly and maintenance, and can remain “asleep” when not in use, thus reducing the visual impact on the environment. This turbine makes use of the force of the wind to control itself, simplifying the manufacture of large turbines connected to the network or in isolated applications.

Abstract: A compressor for receiving at least one compression element in a sealed container is provided. The sealed container comprises a container body and a cover member for blocking an opening of the container body, both of which are made of an aluminum material. The cover member is electrically welded to the container body over an entire circumference of the cover member, and thick ribs with a thickness dimension extending from a circumference portion to a central portion are formed with a predetermined pitch on the cover member. In this manner, an increase in the manufacturing cost and a reduction of the workability can be substantially suppressed, while the reliability of the sealed container of the compressor and the aluminum members assembled by arc welding can be substantially improved.

Abstract: A pump assembly 1, 33, 200 adapted for continuous flow pumping of blood. In a particular form the pump 1, 200 is a centrifugal pump wherein the impeller 100, 204 is entirely sealed within the pump housing 2, 201 and is exclusively hydrodynamically suspended therein as the impeller rotates within the fluid 105 urged by electromagnetic means external to the pump cavity 106, 203. Hydrodynamic suspension is assisted by the impeller 100, 204 having deformities therein such as blades 8 with surfaces tapered from the leading edges 102, 223 to the trailing edges 103, 224 of bottom and top edges 221, 222 thereof.

Abstract: Apparatus (10) controls net thrust in a steam turbine (T) in response to changes in the operating condition of the turbine. The turbine includes a thrust bearing (B) positioned between low and intermediate pressure sections (LP, IP) of the turbine and a high pressure section (HP) thereof. Sensors (14) for sense thrust loads on the thrust bearing. A number of control valve (CV1-CV4) are used to balance pressures occurring at locations within the high pressure section of the turbine. A controller (16) is responsive to the sensors sensing a change within the turbine indicative of a significant change in net thrust to energize one or more of the control valves and to adjust the pressure within the high pressure section of the turbine so to maintain net thrust within an acceptable range of thrust values.

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum longitudinally located within the leading edge of the airfoils. Within the plenum are positioned a plurality of turbulence promoters to provide enhance heat transfer within the leading edge. Also, the cooling design includes a plurality of inlets to receive cooling air from an internal cavity of the airfoil as well as a plurality of outlets located within a trench on the exterior surface of the leading edge through which the cooling air exits to film cool leading edge.

Abstract: Disclosed is a system for operating gas turbine engine bleed valves in response to pressure values within the engine, wherein the engine pressure values are sensed electronically and routed to a programmable logic device, and wherein the programmable logic device control the opening and closing of the bleed valves in a manner that allows for reduced engine vibration with minimal loss of engine efficiency.

Abstract: A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.

Abstract: An exhaust adapter for use with a draft inducer having a blower housing with a rectangular blower outlet. The exhaust adapter provides a transition from the rectangular outlet of the blower housing and a round exhaust pipe. The exhaust adapter includes a transition section extending between an attachment flange and a round exhaust outlet. The exhaust adapter thus facilitates attachment of the blower housing to a round exhaust pipe. The exhaust adapter is formed from two sections of stamped metal joined to each other along a top and a bottom seam. The two sections of stamped metal allow the exhaust adapter to be formed using inexpensive materials and an inexpensive manufacturing process.

Abstract: A cooled turbine shroud segment for a gas turbine engine, having an axially extending shroud ring segment with an inner surface, an outer surface, an upstream flange and a downstream flange. The flanges mount the shroud ring within an engine casing. A perforated cooling air impingement plate is disposed on the outer surface of the shroud ring between the upstream flange and the downstream flange, with an impingement plenum defined between the impingement plate and the outer surface. Axially extending cooling bores in the ring segment extend between the impingement plenum and an outlet. A trough adjacent the outlet directs cooling air from the outlet towards a downstream stator vane to cool the stator vane.

Abstract: A centrifugal blower impeller includes a central hub and a plurality of impeller blades. The central hub includes a conical section and an outer edge. The conical section is centered with respect to a center axis and extends from the center axis towards the outer edge. The plurality of impeller blades includes first and second ends. The conical section is coupled to the first ends of the impeller blades which extend axially upward from the first ends towards the second ends. The centrifugal blower impeller also includes a rim which has a generally circular shape and is connected to the second ends of the impeller blades.

Abstract: A regenerative fuel pump comprising a housing, a pump cover having a first flow channel formed therein, a pump body having a second flow channel formed therein whereby the first flow channel and the second flow channel define a pumping chamber, and an impeller mounted between the pump cover and pump body and including a plurality of vanes spaced circumferentially about the impeller and defining a plurality of vane grooves. The vanes are spaced un-evenly in a non-repeating pattern about the impeller. The first and second flow channels each include an inlet end, an outlet end, and a stripper area defined as the area between the inlet end and the outlet end extending from the inlet end away from the flow channel. Each of the stripper areas including a plurality of grooves formed therein adapted to dampen pressure pulsations within the pumping chamber.

Abstract: A vacuum pump has a pump case having a gas suction port at an upper surface thereof, a rotor shaft mounted in the pump case for undergoing rotation, and a rotor connected to the rotor shaft for rotation therewith. The rotor has inner and outer circumferential surfaces coated with a corrosion-resistant film treated by nonelectrolytic plating. Rotor blades are disposed in the pump case and are integrally connected to the outer circumferential surface of the rotor. Stator blades are integrally connected to the pump case so that the rotor blades and the stator blades are alternately positioned and arranged. A balancing body is disposed on the inner circumferential surface of the rotor for balancing the rotor during rotation thereof.

Abstract: Aspects of the present invention relate to hollow elongated turbine engine components, such as transition ducts, having a cooling system. The component can have first and second ends, and can be defined by an outer peripheral wall. The cooling system extends longitudinally within the wall between the first and second ends. While configured to cool the entire component, the cooling system is particularly configured to reduce thermal gradients that can occur in regions proximate to the first and second ends of the component caused by higher loads in those regions. The cooling system can include at least one pair of cooling channels. Each channel pair includes a first channel and a second channel. The first and second channels can be arranged such that a coolant supplied to each channel can exchange heat with itself in at least the region substantially proximate to one of the ends.

Abstract: A heat dispensing fan includes a hub having a recess defined in a top thereof so as to receive a fan member therein. The recess communicates with a side outlet in the hub and apertures defined through the hub. The fan member has a ring-shaped base plate and a protrusion extends from a center of a top of the base plate. A plurality of first curve blades extends from the protrusion and a plurality of second curve blades are located on the top of the base plate. Each first curve blade is connected to one of the second curve blades. A top cap is connected to the hub and has a hole defined therethrough.

Abstract: A fan assembly for use in association with an airborne vehicle, the fan assembly comprising a propeller assembly and a shroud. The propeller assembly is rotatably coupled to an output shaft of a motor. The propeller assembly includes at least two blades each having a first end proximate an output shaft of a motor and a second end distally spaced therefrom. The shroud extends circumferentially around the propeller assembly, and includes a groove along the lower surface thereof. In turn, the second end of the at least two blades extends at least partially into the groove.

Abstract: A stator vane span attachment for a gas turbine having a casing 1 in which several stator vane spans 2 are located, wherein means 3 are provided for restraining the stator vane spans 2 against the casing 1.